Variable geometry turbine

ABSTRACT

A variable geometry turbine comprises: a turbine wheel in a housing for rotation about a turbine axis; an annular inlet passage defined between respective radial inlet surfaces of first and second wall members, at least one of said first and second wall members being moveable along the turbine axis to vary the size of the inlet passage; an array of vanes extending across the inlet passage, said vanes being connected to said first wall member; a complementary array of vane slots defined by the second wall member, said vane slots configured to receive said vanes to accommodate relative movement between the first and second wall members; the second wall member comprising at least two axially adjacent co-axial plates, a first plate defining a first array of openings which overlie a second array of openings defined by a second plate so as to define said array of vane slots, said first plate being fixed to said second plate.

The present invention relates to a variable geometry turbine.Particularly, but not exclusively, the present invention relates tovariable geometry turbochargers.

A conventional turbine essentially comprises an exhaust gas driventurbine wheel mounted on a rotatable shaft within a turbine housingconnected downstream of an engine outlet manifold. Rotation of theturbine wheel drives either a compressor wheel mounted on the other endof the shaft within a compressor housing to deliver compressed air to anengine intake manifold, or a gear which transmits mechanical power to anengine flywheel or crankshaft. The turbine shaft is conventionallysupported by journal and thrust bearings, including appropriatelubricating systems, located within a bearing housing.

Turbochargers are well known devices for supplying air to the intake ofan internal combustion engine at pressures above atmospheric pressure(boost pressures). In turbochargers, the turbine stage comprises aturbine chamber within which the turbine wheel is mounted; an annularinlet passageway defined between opposite radial walls arranged aroundthe turbine chamber; an inlet arranged around the inlet passageway; andan outlet passageway extending from the turbine chamber. The passagewaysand chambers communicate such that pressurised exhaust gas admitted tothe inlet chamber flows through the inlet passageway to the outletpassageway via the turbine and rotates the turbine wheel. Turbineperformance can be improved by providing vanes, referred to as nozzlevanes, in the inlet passageway so as to deflect gas flowing through theinlet passageway towards the direction of rotation of the turbine wheel.

Turbines may be of a fixed or variable geometry type. Variable geometryturbines differ from fixed geometry turbines in that the size of theinlet passageway can be varied to optimise gas flow velocities over arange of mass flow rates so that the power output of the turbine can bevaried to suite varying engine demands. For instance, when the volume ofexhaust gas being delivered to the turbine is relatively low, thevelocity of the gas reaching the turbine wheel is maintained at a levelwhich ensures efficient turbine operation by reducing the size of theannular inlet passageway. Turbochargers provided with a variablegeometry turbine are referred to as variable geometry turbochargers.

In one known type of variable geometry turbine, an axially moveable wallmember, generally referred to as a “nozzle ring”, defines one wall ofthe inlet passageway. The position of the nozzle ring relative to afacing wall of the inlet passageway is adjustable to control the axialwidth of the inlet passageway. Thus, for example, as gas flows throughthe turbine decreases, the inlet passageway width may be decreased tomaintain gas velocity and optimise turbine output. This arrangementdiffers from another type of variable geometry turbine in which avariable guide vane array comprises adjustable swing guide vanesarranged to pivot so as to open and close the inlet passageway.

The nozzle ring may be provided with vanes which extend into the inletand through vane slots provided in a “shroud” defining the facing wallof the inlet passageway to accommodate movement of the nozzle ring.Alternatively vanes may extend from the fixed facing wall and throughvane slots provided in the nozzle ring.

Typically the nozzle ring may comprise a radially extending wall(defining one wall of the inlet passageway) and radially inner and outeraxially extending walls or flanges which extend into an annular cavitybehind the radial face of the nozzle ring. The cavity is formed in apart of the turbocharger housing (usually either the turbine housing orthe turbocharger bearing housing) and accommodates axial movement of thenozzle ring. The flanges may be sealed with respect to the cavity wallsto reduce or prevent leakage flow around the back of the nozzle ring.

In one common arrangement of a variable geometry turbine the nozzle ringis supported on rods extending parallel to the axis of rotation of theturbine wheel and is moved by an actuator which axially displaces therods. Nozzle ring actuators can take a variety of forms, includingpneumatic, hydraulic and electric and can be linked to the nozzle ringin a variety of ways. The actuator will generally adjust the position ofthe nozzle ring under the control of an engine control unit (ECU) inorder to modify the airflow through the turbine to meet performancerequirements.

As mentioned above, as the nozzle ring is moved to adjust the axialwidth of the inlet passageway, the guide vanes may extend intoaccurately defined vane slots in a shroud plate to accommodate themovement. Typically, shroud plates are made by turning from bar, whereeach plate is essentially a disc of material, often provided with acircumferential groove extending around the periphery of the disc toaccommodate a locating ring which retains the disc within the turbinehousing. After turning, the vane slots are usually produced in the disc,one at a time, by numerical control (NC) laser cutting. In order toensure efficient functioning of the nozzle ring and shroud plateassembly it is important that the size, shape and position of the vaneslots accurately matches that of the guide vanes. This introduces veryfine tolerances to the manufacture of both the shroud plate and thenozzle ring carrying the guide vanes. Production of shroud plates andnozzle rings is therefore an undesirably complicated and costly processrequiring very careful control of a number of different manufacturingprocesses to ensure the two components function together satisfactorily.

It is an object of the present invention to obviate or mitigate one ormore of the problems set out above.

According to a first aspect of the present invention there is providedvariable geometry turbine comprising:

a turbine wheel supported in a housing for rotation about a turbineaxis;

an annular inlet passage defined between respective radial inletsurfaces of first and second wall members, at least one of said firstand second wall members being moveable along the turbine axis to varythe size of the inlet passage;

an array of vanes extending across the inlet passage, said vanes beingconnected to said first wall member;

a complementary array of vane slots defined by the second wall member,said vane slots being configured to receive said vanes to accommodaterelative movement between the first and second wall members;

wherein the second wall member comprises at least two axially adjacentco-axial plates, a first of said plates defining a first array ofopenings which overlie a second array of openings defined by a second ofsaid plates so as to define said array of vane slots, said first platebeing fixed to said second plate.

Forming the second wall member from at least two axially adjacentco-axial plates is advantageous since it can simplify the process ofproducing the wall member with the appropriate dimensions andarrangement of vanes slots to suit a particular application. Preferablythe co-axial plates are concentrically arranged with respect to oneanother. Moreover, the plates are preferably annular in shape.

In a preferred embodiment the cross-sectional shape transverse to saidturbine axis of at least one of the openings in said first array ofopenings more closely matches the cross-sectional shape transverse tosaid turbine axis of the vane that said at least one opening is arrangedto receive than the cross-sectional shape transverse to said turbineaxis of at least one of the openings in said second array of openings.Providing at least one of the openings in the second plate with across-sectional shape which less closely matches the cross-sectionalshape of the vane which it is intended to receive, enables cheaper andsimpler manufacturing processes to be used in the manufacture of thesecond plate. For example, while the cross-sectional shape of theopenings in the first plate is preferably very similar to thecross-sectional shape of the vane which the opening was intended toreceive, the underlying opening in the second plate may have arelatively simple cross-sectional shape such as a round, square,rectangular or oval shape provided the opening in the second plate issufficiently large to encompass the overlying opening in the firstplate. Thus it is preferred that said at least one opening in said firstarray of openings may axially overlie said at least one opening in saidsecond array of openings to define one slot of said array of vanesslots.

In a preferred example, the openings in the second plate have asubstantially rectangular cross-sectional shape but with the short edgesof the rectangle being curved for ease of manufacture.

In a further preferred embodiment said first plate may be substantiallyrotationally and/or radially fixed relative to said second plate.Preferably the first plate is substantially fixed both rotationally andradially relative to the second plate. The first and second plates maybe laminated together. Moreover, the first and second plates may befixed together by an adhesive, braze, rivet, screw, weld or the like.

One of said first and second plates may define at least one axiallyextending projection, such as a semi-shear or locating pin, configuredfor receipt in a complementary recess defined by the other of the firstand second plates.

The first and second plates may be positioned axially relative to thefirst wall member to suit a particular application. For certainapplications it may be preferable for the first plate may be positionedaxially closer to said first wall member than said second plate, or forsaid second plate to be positioned axially closer to said first wallmember than said first plate.

The second wall member may comprise any number of additional co-axial orconcentric plates. Thus, the second wall member may comprise at least athird co-axial or concentric plate that is axially adjacent to saidsecond plate, said third plate defining a third array of openings whichoverlie the second array of openings defined by the second plate so asto further define said array of vane slots. The third plate may beannular in shape. It is thus preferred that the second plate isinterposed between the first and third plates.

In order to further simplify and reduce the cost of manufacturing thethird (and any subsequent) co-axial or concentric plates, it ispreferred that the cross-sectional shape transverse to said turbine axisof at least one of the openings in said first array of openings moreclosely matches the cross-sectional shape transverse to said turbineaxis of the vane that said at least one opening is arranged to receivethan the cross-sectional shape transverse to said turbine axis of atleast one of the openings in said third array of openings.

The cross-sectional shape of the third array of openings may be the sameor may differ from the cross-sectional shape of the second array ofopenings. Thus, said cross-sectional shape transverse to said turbineaxis of at least one of the openings in said third array of openings maysubstantially match the cross-sectional shape transverse to said turbineaxis of at least one of the openings in said second array of openings.

Preferably said at least one opening in said third array of openingsaxially overlies said at least one opening in said second array ofopenings to further define one slot of said array of vanes slots.

Preferably the third plate is fixed to the second plate.

The third plate may be laminated to the second plate. Moreover, thethird plate may be fixed to the second plate by an adhesive, braze,rivet, screw, weld or the like.

One of said second and third plates may define at least one furtheraxially extending projection (e.g. semi-shear or locating pin)configured for receipt in a complementary recess defined by the other ofthe second and third plates.

The second wall member may be supported within a turbine housing in anyappropriate manner provided the means of fixing the second wall memberis appropriate for the particular application.

Said second wall member may define a circumferential groove extendingaround the radially outermost edge of the second wall member, saidgroove arranged to receive a locating ring to retain the second wallmember within the turbine housing. This may be achieved by the first andthird plates possessing larger respective diameters than the secondplate, such that the difference in the diameters of the three plates atleast partly defines said circumferential groove.

Rather than using a locating ring the second wall member may beconnected to a turbine housing using some form of fastener such as abolt, rivet or the like. In this case, it may be advantageous to form atleast one of the plates making up the second wall member so as to definea larger outer diameter than one or more of the other plates making upthe second wall member such that one or more fasteners can be insertedthrough the radially extended portion of the larger plate and into theturbine housing thereby fixing the second wall member to the housing.

In a second aspect of the present invention there is provided a variablegeometry turbine comprising:

a turbine wheel supported in a housing for rotation about a turbineaxis;

an annular inlet passage defined between respective radial inletsurfaces of first and second wall members, at least one of said firstand second wall members being moveable along the turbine axis to varythe size of the inlet passage;

an array of vanes extending across the inlet passage, said vanes beingconnected to said first wall member;

a complementary array of vane slots defined by the second wall member,said vane slots being configured to receive said vanes to accommodaterelative movement between the first and second wall members;

wherein the second wall member comprises at least two axially adjacentco-axial plates, a first of said plates defining a first array ofopenings which overlie a second array of openings defined by a second ofsaid plates so as to define said array of vane slots, and furtherwherein said first plate is rotationally and/or radially moveablerelative to said second plate.

In this way, the precise positioning of the first array of openingsrelative to the second array of openings can be adjusted, which willthereby adjust the location of the vanes slots defined by theoverlapping regions of the first and second arrays of openings. Thisallows the arrangement of vane slots in the second wall member to beoptimised for a particular array of vanes connected to the first wallmember. This is advantageous since it allows the array of vanes to bemanufactured to a wider tolerance thereby reducing the cost andcomplexity of manufacturing the first wall member and array of vanes.

In a preferred embodiment the second plate is positioned axially closerto the first wall member than the first plate. This results in thesecond plate facing into the inlet passage of the turbine. Thus, inembodiments in which the cross-sectional shape of the openings in thefirst array of openings more closely matches that of the vanes than thesecond array of openings, it is the second array of openings which isexposed to gases flowing through the inlet passage of the turbine ratherthan the first array of openings. In certain embodiments this willresult in openings in the second plate of larger cross-sectional areafacing into the inlet passageway and the openings in the first plate ofsmaller cross-sectional area facing in the opposite direction towardsthe wall of the turbine housing to which the first wall member isconnected.

It is preferred that said second plate is substantially rotationallyand/or radially fixed relative to said turbine housing. It isparticularly preferred that the second plate is substantially fixed bothrotationally and radially to the turbine housing, for example using asuitable type of fastener such as a bolt, rivet or the like.

In one embodiment the second plate may have a larger diameter than thefirst plate such that a region of the second plate extends radiallybeyond the circumferential edge of the first plate, said region of thesecond plate cooperating with one or more fasteners to fasten saidsecond plate to the turbine housing. Any desirable number of fastenersof any suitable type could be used but it is envisaged that it may beadvantageous to use at least three or four bolts received in aperturesdefined by the region of the second plate which extends radially beyondthe circumferential edge of the first plate.

It will be appreciated that it is important to ensure that the first andsecond plates can move relative to one another without causingundesirable levels of wear to either plate. Moreover, undesirably highlevels of friction between the plates may damage them making themsusceptible to failure and/or corrosion. Thus, a surface of at least oneof the first and second plates which faces the other of the first andsecond plates may be provided with an anti-wear, anti-friction and/oranti-corrosion coating.

In the second aspect of the invention where the first plate isrotationally and/or radially moveable relative to the second plate, thismay only be possible during initial optimisation of the second wallmember for use with a particular first wall member and array of vanes.By way of example, a braze could be applied between the first and secondplates and the vanes inserted into their corresponding vane slots at asufficiently high temperature such that the braze remain sufficientlyfluid to permit relative rotational and/or radial movement between theplates. Once the optimum relative position of the first plate relativeto the second plate has been determined for that particular array ofvanes, the temperature of the second wall member could then be decreasedsuch that the braze solidifies and thereby fixed the first and secondplates together such that rotational and/or radial movement is no longerpossible. Alternatively, the first and second plates may be arranged soas to permit free rotational and/or radial movement throughout thelifetime of use of the turbine.

In a still further preferred embodiment of the first aspect of thepresent invention, said first plate may comprise first and secondsegments defining respective first and second openings from said firstarray of openings, said first segment being displaceable relative tosaid second segment within a major plane of the first plate.

In this embodiment the first plate is formed in segments which aredisplaceable relative to one another so that their optimum displacementrelative to a particular nozzle ring can be readily determined. Thisembodiment therefore affords a further method for optimising thearrangement of vane slots in the second wall member for receipt of vanesfrom a particular first wall member. As mentioned above, adjustment maybe carried out initially prior to use, for example in combination withbrazing the first and second plates together, or a suitable anti-wear,anti-frictional, anti-corrosion coating may be provided on one or moreof the segments so that they can move freely relative to one anotherwithin the major plane of the first plate throughout use of the turbine.

Each of said segments may comprise generally radially extending leadingand trailing edges connected by radially inner and outer edges. Aclearance may be defined between the leading edge of one segment and thetrailing edge of a neighbouring segment. This clearance can thenaccommodate relative displacements between neighbouring segments.

Said radially inner and outer edges may possess different lengths.Preferably said radially inner edge is shorter than said radially outeredge. Thus, it is preferred that each segment is flared from itsradially inner edge to its radially outer edge.

Said leading and trailing edges may be swept forward relative to saidradial line. The leading edge may be swept forward to a greater extentthan the trailing edge.

At least one of said leading and trailing edges may be curved relativeto a radial line passing through said segment and the turbine axis.Moreover at least one of said inner and outer edges of each segment maybe curved.

It is thus preferred that each segment of the first plate has ascimitar-like cross-sectional shape as can be seen in the specificembodiments described below in relation to FIGS. 14A, 14B and 15.

Preferably both of said inner and outer edges of each segment arecurved, and said inner and outer edges possess a substantially similarcurvature.

In a preferred version of the present embodiment, said second platecomprises first and second segments defining respective first and secondopenings from said second array of openings, said first segment of thesecond plate being displaceable relative to said second segment of thesecond plate within a major plane of the second plate.

Said first segment of the first plate may axially overlie said firstsegment of the second plate. Preferably overlying segments from thefirst and second plates are connected together such that rotationaland/or radial displacement of a segment relative to the segment itoverlies is prevented. Any suitable type of connection between overlyingsegments may be used, such as brazing.

In a similar fashion to the segments of the first plate, each of saidsegments of the second plate may comprise generally radially extendingleading and trailing edges connected by radially inner and outer edges.

Preferably a further clearance is defined between the leading edge ofone segment and the trailing edge of a neighbouring segment. Saidfurther clearance can accommodate relative displacement of segments ofthe second plate. Where overlying segments of the first and secondplates are connected together so as to move in unison, it is preferablethat the clearances defined between segments of the first plate andsegments of the second plate are similar in shape so as to afford asimilar degree of relative movement between segments in the first plateand segments in the second plate.

Said first segment of the second plate may be circumferentially offsetwith respect to said first segment of the first plate such that saidclearance defined between segments of the first plate iscircumferentially offset with respect to said further clearance definedbetween segments of the second plate. In this way the clearances definedbetween segments of the first plate do not axially overlie clearancesdefined between segments of the second plate so as to avoid presenting aleak path for gases flowing through the turbine inlet passageway.

The major plane of the first plate and/or second plate may besubstantially orthogonal to the turbine axis.

It is preferred that said first plate is positioned axially closer tosaid first wall member than said second plate.

The periphery of the second plate may be received within a radiallyextending channel defined by the turbine housing. The second plate maypossess a larger diameter than the first plate such that a region of thesecond plate may be located radially outwardly of the first plate, atleast part of said region being retained within said channel by aretaining member. Said retaining member may be positioned axially closerto said first wall member than said second plate. Said retaining membermay be fastened to the turbine housing. The means of fastening may takeany appropriate form, such as bolts, rivets and/or screws. Moreover anydesirable number and/or arrangement of fasteners may be employed. By wayof example only, it is envisaged that providing the retaining memberwith four equally angularly spaced apertures to receive suitablefasteners may be suitable.

At least one of the co-axial or concentric plates comprised in thesecond wall member may be formed from stainless steel.

According to a third aspect of the present invention there is provided avariable geometry turbine comprising:

a turbine wheel supported in a housing for rotation about a turbineaxis;

an annular inlet passage defined between respective radial inletsurfaces of first and second wall members, at least one of said firstand second wall members being moveable along the turbine axis to varythe size of the inlet passage;

an array of vanes extending across the inlet passage, said vanes beingconnected to said first wall member;

a complementary array of vane slots defined by the second wall member,said vane slots being configured to receive said vanes to accommodaterelative movement between the first and second wall members;

wherein the second wall member comprises a first plate defining a firstarray of openings so as to define said array of vane slots, said firstplate comprising first and second segments defining respective first andsecond openings from said first array of openings, said first segmentbeing displaceable relative to said second segment within a major planeof the first plate.

Preferably the first plate is annular in shape.

Each of said segments may comprise generally radially extending leadingand trailing edges connected by radially inner and outer edges. Aclearance may be defined between the leading edge of one segment and thetrailing edge of a neighbouring segment. This clearance can thenaccommodate relative displacements between neighbouring segments.

Said radially inner and outer edges may possess different lengths.Preferably said radially inner edge may be shorter than said radiallyouter edge. Thus, it is preferred that each segment is flared from itsradially inner edge to its radially outer edge.

Said leading and trailing edges may be swept forward relative to saidradial line. The leading edge may be swept forward to a greater extentthan the trailing edge.

At least one of said leading and trailing edges may be curved relativeto a radial line passing through said segment and the turbine axis.Moreover at least one of said inner and outer edges of each segment maybe curved.

It is thus preferred that each segment of the first plate has ascimitar-like cross-sectional shape as can be seen in the specificembodiments described below in-relation to FIGS. 14A, 14B and 15.

Both of said inner and outer edges of each segment may be curved, andsaid inner and outer edges may possess a substantially similarcurvature.

The major plane of the first plate may be substantially orthogonal tothe turbine axis.

The first plate comprised in the second wall member may be formed fromany suitable material, such as stainless steel.

In a preferred embodiment of the third aspect, the second wall membercomprises a second plate which is positioned axially adjacent to thefirst plate and said second plate being arranged co-axially orconcentrically with respect to said first plate, the first platedefining a first array of openings which overlie a second array ofopenings defined by the second plate so as to define said array of vaneslots.

In a preferred example of this embodiment the cross-sectional shapetransverse to said turbine axis of at least one of the openings in saidfirst array of openings may more closely match the cross-sectional shapetransverse to said turbine axis of the vane that said at least oneopening is arranged to receive than the cross-sectional shape transverseto said turbine axis of at least one of the openings in said secondarray of openings.

In this way, the openings in the second array of openings can bemanufactured to a wider tolerance than those in the first array whichare intended to closely match the cross-sectional shape of the vaneswhich the slots defined by the overlapping openings are intended toaccommodate. As mentioned above in respect of other embodiments of thefirst and second aspects of the present invention, allowing one of theplates making up the second wall member to be manufactured to a widertolerance reduces the cost and complexity of manufacturing thiscomponent.

Said at least one opening in said first array of openings may axiallyoverlie said at least one opening in said second array of openings todefine one slot of said array of vanes slots.

In a preferred version of the present embodiment, said second platecomprises first and second segments defining respective first and secondopenings from said second array of openings, said first segment of thesecond plate being displaceable relative to said second segment of thesecond plate within a major plane of the second plate.

Said second plate comprises first and second segments definingrespective first and second openings from said second array of openings,said first segment of the second plate being displaceable relative tosaid second segment of the second plate within a major plane of thesecond plate.

Said first segment of the first plate may axially overlie said firstsegment of the second plate. Preferably overlying segments from thefirst and second plates are connected together such that rotationaland/or radial displacement of a segment relative to the segment itoverlies is prevented. Any suitable type of connection between overlyingsegments may be used, such as brazing.

In a similar fashion to the segments of the first plate, each of saidsegments of the second plate may comprise generally radially extendingleading and trailing edges connected by radially inner and outer edges.

A further clearance may be defined between the leading edge of onesegment and the trailing edge of a neighbouring segment. Said furtherclearance can accommodate relative displacement of segments of thesecond plate. Where overlying segments of the first and second platesare connected together so as to move in unison, it is preferable thatthe clearances defined between segments of the first plate and segmentsof the second plate are similar in shape so as to afford a similardegree of relative movement between segments in the first plate andsegments in the second plate.

Said first segment of the second plate may be circumferentially offsetwith respect to said first segment of the first plate such that saidclearance defined between segments of the first plate iscircumferentially offset with respect to said further clearance definedbetween segments of the second plate. In this way the clearances definedbetween segments of the first plate do not axially overlie clearancesdefined between segments of the second plate so as to avoid presenting aleak path for gases flowing through the turbine inlet passageway.

The major plane of the second plate may be substantially orthogonal tothe turbine axis.

In an additional embodiment of the first aspect of the present inventionwherein at least the first plate is segmented, it is preferred that saidfirst plate may be positioned axially closer to said first wall memberthan said second plate.

The periphery of the second plate may be received within a radiallyextending channel defined by the turbine housing. The second plate maypossess a larger diameter than the first plate such that a region of thesecond plate may be located radially outwardly of the first plate, atleast part of said region being retained within said channel by aretaining member. Said retaining member may be positioned axially closerto said first wall member than said second plate. Said retaining membermay be fastened to the turbine housing.

The means of fastening may take any appropriate form, such as bolts,rivets and/or screws. Moreover any desirable number and/or arrangementof fasteners may be employed. By way of example only, it is envisagedthat providing the retaining member with four equally angularly spacedapertures to receive suitable fasteners may be suitable.

The second plate comprised in the second wall member may be formed fromany suitable material such as, stainless steel.

The array of vane slots may be provided as a substantially annular arrayof vane slots. The vane slots comprised in said annular array of vaneslots may be substantially equi-angularly spaced.

One of said first and second wall members may be axially moveable andthe other of said first and second may be fixed. Said fixed wall membermay be defined by a facing wall of said housing.

According to a fourth aspect of the present invention there is provideda method for assembling a shroud plate for a variable geometry turbine,said shroud plate comprising at least two plates, the method comprisingaligning a first of said plates with a second of said plates such that afirst array of openings defined by the first plate overlies a secondarray of openings defined by the second plate so as to define an arrayof vane slots.

Preferably said at least two plates are concentrically aligned withrespect to one another.

The shroud plate forming part of the fourth aspect of the presentinvention may be considered as the second wall member of the firstaspect of the present invention. Moreover, in the preferred embodimentsof the third aspect of the present invention employing at least twoplates to form the second wall member, the method according to thefourth aspect of the present invention defined above is equallyapplicable.

Preferably the plates are concentric and/or may be arranged such that,when mounted within a turbine, they are co-axially aligned. Alignment ofthe first and second plates may comprise locating at least oneprojection such as a semi-shear or locating pin defined by one of saidfirst and second plates within a complementary recess defined by theother of the first and second plates.

In a first preferred embodiment of the fourth aspect of the presentinvention, following alignment of the first and second plates, saidplates are fixed together such that said first plate is substantiallyfixed rotationally and/or radially relative to said second plate. Theplates may be fixed together by an adhesive, braze, rivet, screw, weldor the like. In another preferred embodiment, following alignment of thefirst and second plates, the plates are laminated together such thatsaid first plate may be substantially fixed rotationally and/or radiallyrelative to said second plate.

In a further preferred embodiment alignment of the first and secondplates may comprise inserting first and second vanes connected to avariable geometry turbine nozzle ring into respective first and secondvane slots from said array of vane slots. During and/or followinginsertion of said vanes into said vane slots, one of the plates may berotated and/or radially displaced relative to the other of the plates toadjust the degree to which the first array of openings overlie thesecond array of openings so as to change the position of the first vaneslot relative to the second vane slot. In this way, the relativeorientation between slots can be optimised to suit a particular array ofvanes connected to a turbine nozzle ring. Optimisation may be carriedout prior to use of the turbine, in which case the first and secondplates may be fixed together in the optimised configuration followingadjustment. Alternatively, the plates may retain the ability to moverelative to one another during use of the turbine so that optimisationis essentially carried out each time the array of vanes is inserted intothe vane slots.

In a still further preferred embodiment said first plate may comprisefirst and second segments defining respective first and second openingsfrom said first array of openings, said first segment being displaceablerelative to said second segment within a major plane of the first plate,the method further comprising displacing said first segment relative tosaid second segment within the major plane of the first plate duringand/or following insertion of said vanes into said vane slots to adjustthe position of the first segment relative to the second segment so asto change the position of the first vane slot relative to the secondvane slot. Segmenting the first plate forming part of the shroud plateenables the relative arrangement of vane slots to be optimised to matchthe arrangement of vanes on a turbine nozzle ring. As mentioned above inrespect of the previous preferred embodiment, optimisation may becarried out before use of the turbine after which the segments of thefirst plate are fixed relative to one another, or the segments mayremain displaceable throughout the lifetime of the turbine such thatoptimisation is carried out each time a vane is attached to a two linenozzle ring into the vane slots.

The or each plate which forms part of the shroud plate may be formedfrom any desirable material in any appropriate manner. For example, atleast one of the plates may be formed by stamping from a rolled strip ofstainless steel.

According to a fifth aspect of the present invention there is provided amethod for preparing a shroud plate for use in a variable geometryturbine, said shroud plate comprising a first plate defining a firstarray of openings so as to define an array of vane slots, and said firstplate comprising first and second segments defining respective first andsecond openings from said first array of openings, said first segmentbeing displaceable relative to said second segment within a major planeof the first plate, wherein the method comprises inserting first andsecond vanes connected to a variable geometry turbine nozzle ring intorespective first and second vane slots from said array of vane slots,and displacing said first segment relative to said second segment withinthe major plane of the first plate during and/or following insertion ofsaid vanes into said vane slots so as to adjust the position of thefirst segment relative to the second segment such that the position ofthe first vane slot relative to the second vane slot more closelymatches the position of the first vane relative to the second vane thanbefore adjustment of the relative position of the first and secondsegments.

The fifth aspect of the present invention employs a segmented plate witha plurality of segments which can move relative to one another so as topermit optimisation of the relative displacement in relation to an arrayof vanes connected to a variable geometry turbine nozzle ring. Asmentioned above in connection with previous aspects of the presentinvention, such optimisation can be carried out once before the turbineis used and the segments then fixed together in their optimisedorientation or the segments can remain free to move relative to oneanother such that optimisation is essentially carried out each time thearray of vanes is inserted into the vane slots defined by the shroudplate.

Other advantageous and preferred features of the invention will beapparent from the following description.

Specific embodiments of the present invention will now be described, byway of example only, with reference to the accompanying drawings, inwhich:

FIG. 1 is an axial cross-section through a known variable geometryturbocharger;

FIG. 2A is a front view of a prior art shroud plate for use in avariable geometry turbine;

FIG. 2B is a cross-sectional view taken along line G-G of the shroudplate of FIG. 2A;

FIG. 3A is a front view of a shroud plate according to a firstembodiment of the present invention;

FIG. 3B is a cross-sectional view of the shroud plate of FIG. 3A;

FIG. 4A is a front view of a front plate of the shroud plate of FIGS. 3Aand 3B.

FIG. 4B is a cross-sectional view of the front plate of FIG. 4A;

FIG. 5A is a front view of an intermediate plate of the shroud plate ofFIGS. 3A and 3B;

FIG. 5B is a cross-sectional view of the intermediate plate of FIG. 5A;

FIG. 6A is a front view of a back plate of the shroud plate of FIGS. 3Aand 3B;

FIG. 6B is a cross-sectional view of the back plate of FIG. 6A;

FIG. 7 is a cross-sectional view of a shroud plate according to a secondembodiment of the present invention;

FIG. 8A is a cross-sectional view of an upper portion of the shroudplate of FIG. 7 supported within a turbine housing;

FIG. 8B is a cross-sectional view of a lower portion of the shroud plateof FIG. 7 supported within the turbine housing;

FIG. 9 is a front view of a back plate of a shroud plate according to athird embodiment of the present invention;

FIG. 10 is a front view of a front plate to be used with the back plateof FIG. 9 to form the shroud plate according to a third embodiment ofthe present invention;

FIG. 11 is a cross-sectional view of the shroud plate according to thethird embodiment of the present invention with the back plate of FIG. 9attached to the front plate of FIG. 10;

FIG. 12A is a cross-sectional view of a turbine housing without a shroudplate or nozzle ring;

FIG. 12B is a cross-sectional view of the turbine housing of FIG. 12Awith the shroud plate of FIG. 11 fastened to the turbine housing and anozzle ring located axially adjacent to the shroud plate;

FIG. 13A is a detailed cross-sectional view of the circled portion ofthe turbine housing of FIG. 12A;

FIG. 13B is a detailed cross-sectional view of the circled portion ofFIG. 12B showing the means of connection of the shroud plate of FIG. 11to the turbine housing.

FIG. 14A is a front view of a shroud plate according to a fourthembodiment of the present invention;

FIG. 14B is a perspective view of the shroud plate of FIG. 14A;

FIG. 15 is a front view of a segment of the shroud plate of FIG. 14A;

FIG. 16A is a cross-sectional view of an upper portion of a turbinehousing with the shroud plate of FIG. 14A attached to the housing;

FIG. 16B is a cross-sectional view of the turbine housing and shroudplate of FIG. 16A;

FIG. 17 is a detailed cross-sectional view of the circled region C ofthe turbine housing and shroud plate of FIG. 16A;

FIG. 18A is a cross-sectional view of a shroud plate according to afifth embodiment of the present invention mounted within a turbinehousing; and

FIG. 18B is a perspective view of a section of a segmented annular plateforming part of the shroud plate FIG. 18A.

Referring to FIG. 1, this illustrates a known variable geometryturbocharger comprising a variable geometry turbine housing 1 and acompressor housing 2 interconnected by a central bearing housing 3. Aturbocharger shaft 4 extends from the turbine housing 1 to thecompressor housing 2 through the bearing housing 3. A turbine wheel 5 ismounted on one end of the shaft 4 for rotation within the turbinehousing 1, and a compressor wheel 6 is mounted on the other end of theshaft 4 for rotation within the compressor housing 2. The shaft 4rotates about turbocharger axis 4 a on bearing assemblies located in thebearing housing 3.

The turbine housing 1 defines an inlet volute 7 to which gas from aninternal combustion engine (not shown) is delivered. The exhaust gasflows from the inlet volute 7 to an axial outlet passageway 8 via anannular inlet passageway 9 and the turbine wheel 5. The inlet passageway9 is defined on one side by a face 10 of a radial wall of a moveableannular wall member 11, commonly referred to as a “nozzle ring”, and onthe opposite side by an annular shroud 12 which forms the wall of theinlet passageway 9 facing the nozzle ring 11. The shroud 12 covers theopening of an annular recess 13 in the turbine housing 1.

The nozzle ring 11 supports an array of circumferentially and equallyspaced inlet vanes 14 each of which extends across the inlet passageway9. The vanes 14 are orientated to deflect gas flowing through the inletpassageway 9 towards the direction of rotation of the turbine wheel 5.When the nozzle ring 11 is proximate to the annular shroud 12, the vanes14 project through suitably configured slots in the shroud 12, into therecess 13.

The position of the nozzle ring 11 is controlled by an actuator assemblyof the type disclosed in U.S. Pat. No. 5,868,552. An actuator (notshown) is operable to adjust the position of the nozzle ring 11 via anactuator output shaft (not shown), which is linked to a yoke 15. Theyoke 15 in turn engages axially extending actuating rods 16 that supportthe nozzle ring 11. Accordingly, by appropriate control of the actuator(which may for instance be pneumatic or electric), the axial position ofthe rods 16 and thus of the nozzle ring 11 can be controlled. The speedof the turbine wheel 5 is dependent upon the velocity of the gas passingthrough the annular inlet passageway 9. For a fixed rate of mass of gasflowing into the inlet passageway 9, the gas velocity is a function ofthe width of the inlet passageway 9, the width being adjustable bycontrolling the axial position of the nozzle ring 11. FIG. 1 shows theannular inlet passageway 9 fully open. The inlet passageway 9 may beclosed to a minimum by moving the face 10 of the nozzle ring 11 towardsthe shroud 12.

The nozzle ring 11 has axially extending radially inner and outerannular flanges 17 and 18 that extend into an annular cavity 19 providedin the turbine housing 1. Inner and outer sealing rings 20 and 21 areprovided to seal the nozzle ring 11 with respect to inner and outerannular surfaces of the annular cavity 19 respectively, whilst allowingthe nozzle ring 11 to slide within the annular cavity 19. The innersealing ring 20 is supported within an annular groove formed in theradially inner annular surface of the cavity 19 and bears against theinner annular flange 17 of the nozzle ring 11. The outer sealing ring 20is supported within an annular groove formed in the radially outerannular surface of the cavity 19 and bears against the outer annularflange 18 of the nozzle ring 11.

Gas flowing from the inlet volute 7 to the outlet passageway 8 passesover the turbine wheel 5 and as a result torque is applied to the shaft4 to drive the compressor wheel 6. Rotation of the compressor wheel 6within the compressor housing 2 pressurises ambient air present in anair inlet 22 and delivers the pressurised air to an air outlet volute 23from which it is fed to an internal combustion engine (not shown).

Referring to FIGS. 2A and 2B, there is shown a prior art shroud platefor use in a variable geometry turbine. The shroud plate 24 is annularin shape and defines an annular array of vane slots 25 for receipt ofvanes attached to a nozzle ring of a variable geometry turbine of thekind shown in FIG. 1. The relative positioning of each vane slot 25compared to the other vane slots 25 and the cross-sectional shape ofeach vane slot 25 should be very carefully controlled so as to ensurethat each vane is correctly received within its respective vane slot 25whilst also ensuring that disturbance to airflow passing over the vaneslots 25 is minimised. The shroud plate 24 must therefore bemanufactured to very high intolerances both in terms of the shape andposition of each vane slot 25 to ensure proper functioning of the shroudplate 24 in combination with the nozzle ring (not shown). The shroudplate 24 defines a circumferential slot 26 which extends around theradially outermost edge of the shroud plate 24. The slot 26 receives aring (not shown) to support the shroud plate 24 within a turbinehousing.

The shroud plate 24 is manufactured by turning from bar. Once a blankdisc has been formed, the circumferential slot 26 is then cut into theradially outer edge of the disc. The vane slots 25 are then cut throughthe disc using, for example, laser cutting. Commonly, the vane slots 25are cut sequentially, i.e. one at a time, making the manufacturingprocess relatively lengthy and expensive.

FIGS. 3A and 3B show a first embodiment of a shroud plate 27 inaccordance with the present invention. The shroud plate 27 is again ofgenerally annular form and defines an array of vane slots 28 to receivevanes connected to a nozzle ring of a variable geometry turbine of thekind depicted in FIG. 1.

The shroud plate 27 is composed of three co-axial, concentric plates 29,30, 31 which have been laminated together to prevent any rotational orradial movement of one of the plates relative to the other plates. Theplates 29, 30, 31 may be laminated together in any suitable way, forexample brazing. The centre plate 30 may be coated with a braze (e.g. byelectroless nickel plating) on both radial faces and the two outerplates 29, 31 then pressed into contact before placing the stackedplates 29, 30, 31 in a furnace, followed by appropriate cooling. In theembodiment shown in FIGS. 3A and 3B the plates 29, 30, 31 are arrangedsuch that the plate 29 is the front (or outer) plate which will face aninlet volute of a variable geometry turbine and so it is this plate 29which will be exposed to gas flowing from the inlet volute to an outletpassageway of the turbine. The plate which is intended to face theturbine housing is plate 31 which is commonly referred to as the back(or inner) plate. The back plate 31 defines three axially extendingprojections 32 which are received in complementary recesses 33 definedby the plate 30 which is positioned intermediate the front and backplates 29, 31. The projections 32 can be in the form of locating pins,semi-shears or any other suitable formation which would permit correctalignment of the back and intermediate plates 31, 30. Similarly, theintermediate plate 30 is also provided with a plurality of axiallyextending projections 34 which are received in complementary recesses 35defined by the front plate 29, thereby providing a means to ensurecorrect alignment of the intermediate plate 30 with respect to the frontplate 29.

Similar axially extending projections, such as semi-shears or pins,could be formed in the front plate 29, projecting forwards, away fromthe centre and back plates 30, 31, such that they would project towardsa nozzle ring during use. In this way, these projections could controlthe minimum inlet passage width of a turbine between the nozzle ring andshroud plate 27. Such projections could supplement or replace pads whichare often formed on the radial face of the nozzle ring for the samepurpose, thereby reducing the cost and complexity of manufacturing thenozzle ring.

It can be seen from FIGS. 3A and 3B that the intermediate plate 30possesses a smaller outer diameter than the front and back plates 29,31. This is to provide the shroud plate 27 with a circumferential slot36 extending around its radially outer edge for receipt of a ring (notshown) to support the shroud plate 27 within the turbine housing (notshown). It will be appreciated that circumferential slot 36 is providedto perform essentially the same function as circumferential slot 26 ofthe prior art shroud plate shown in FIGS. 2A and 2B. Each of the threeplates 29, 30, 31 making up the shroud plate 27 of the present inventionwill now be described in more detail.

The front plate 29 shown in FIGS. 4A and 4B defines an annular array ofopenings 37 whose cross-sectional shape and relative annular positioningclosely matches the shape and positioning of vanes of a nozzle ring (notshown) with which the shroud plate 27 will be used. That is, both theopenings 37 and the vanes must be manufactured to a fine tolerance withrespect to one another. In this way, the openings 37 can accommodaterelative axial movement between the shroud plate 27 and the nozzle ring(not shown) but cause minimal disturbance to gas flowing through theinlet volute of the turbine.

The intermediate plate 30 is shown in FIGS. 5A and 5B. It can beobserved in FIG. 5A that the intermediate plate 30 defines an annulararray of openings 38 whose relative annular position is similar to thatof the openings 37 in the front plate 29, however, the cross-sectionalshape of each opening 38 takes a generally rectangular form with curvedshort sides 39 interconnecting long sides 40 of similar length to thelength of each opening 37 in the front plate 29. The general form ofeach opening 38 in the intermediate plate 30 is therefore easier tomanufacture using more robust tooling than the openings 37 in the frontplate 29. The intermediate plate 30 can therefore be manufactured towider tolerances at relatively low cost compared to the front plate 29.

The back plate 31 is shown in FIGS. 6A and 6B, and defines a similarannular array of openings 41 to the array of openings 38 defined by theintermediate plate 30. That is, the relative annular positioning of eachopening 41 in the back plate 31 substantially matches that of the finetolerance openings 37 defined by the front plate 29, but the generalform of each opening 41 in the back plate 31 is generally rectangularwith curved short sides 42 connecting straight long sides 43 whoselength approximates the length of the fine tolerance openings 37 in thefront plate 29. Consequently, the manufacturing tolerances required inrespect of the back plate 31 are wider than those in the front plate 29,making the back plate 31 easier and cheaper to manufacture.

FIG. 7 depicts a second embodiment of a laminated shroud plate. Theshroud plate 44 shown in FIG. 7 is similar in structure to the shroudplate 27 of FIGS. 3A to 6B, however, the shroud plate 44 shown in FIG. 7incorporates a series of locating pins 45, 46 which project axially fromthe front plate 47 and intermediate plate 48 respectively to be receivedin complementary recesses 49, 50 defined by the intermediate plate 48and the back plate 51 respectively. The shroud plate 44 depicted in FIG.7 includes fine tolerance openings 52 in the front plate 47 overlyingwider tolerance openings 53, 54 in the intermediate plate 48 and backplate 51 respectively.

The openings 52, 53, 54 thus define vane slots 55 extending through thefull width of the shroud plate 44.

FIGS. 8A and 8B show how the shroud plate 44 depicted in FIG. 7 issupported within a turbine housing 56 during use. A circumferential slot57 defined around the radially outer edge of the shroud plate 44 isdimensioned to receive a ring 58 which itself is dimensioned to bereceived within an annular channel 59 defined by the turbine housing 56.In this way, the shroud plate 44 is securely supported within an axiallyextending clearance 60 defined by the turbine housing 56 in the correctorientation to receive vanes 61 attached to a nozzle ring (not shown) ofa turbine. Axial movement of the nozzle ring causes the vanes 61 to bereceived through the vane slots 55 and extend into a suitablydimensioned clearance 62 defined by the turbine housing 56.

Referring now to FIGS. 9, 10 and 11 there is shown a third embodimentaccording to the present invention. In FIG. 9 a back plate 63 in theform of an annular ring defines an annular array of openings 64 whichare positioned so as to overlie an annular array of openings 65 in afront plate 66 when the front plate 66 is connected to the back plate 63to form an assembled shroud plate 67, as shown in FIG. 11.

The cross-sectional shape of the openings 64 defined in the back plate63 more closely matches the cross-sectional shape of vanes attached to anozzle ring (not shown) with which the assembled shroud plate 67 isintended to be used than the openings 65 defined by the front plate 66.This embodiment therefore varies from the first two embodimentsdescribed above in relation to FIGS. 3A to 8B in that the two-pieceshroud plate 67 according to the third embodiment positions the finertolerance openings 64 in the back plate 63 and the wider toleranceopenings 65 in the front plate 66 which will face gas flowing throughthe inlet volute of a turbine in which the shroud plate 67 is to beused.

As can be seen from FIGS. 9 to 11, the back plate 63 defines a smallerouter diameter than the front plate 66 such that a radially outer region68 of the front plate 66 extends radially beyond the periphery 69 of theback plate 63. The extended region 68 of the front plate 66 defines fourequally angularly spaced apertures 70 for receipt of fasteners, forexample bolts, rivets or the like (not shown), to fasten the front plate66 of the shroud plate 67 to the turbine housing as described in moredetail below in relation to FIGS. 12A to 13B.

FIG. 12A is a cross-sectional view of a turbine housing 71 prior tolocation of the shroud plate 67 from FIGS. 9 to 11 within the housing71. A more detailed view of the circled area A of FIG. 12A is shown inFIG. 13A. As can be seen from FIGS. 12A and 13A the turbine housing 71defines an annular recess 72 for receipt of the front plate 66 of theshroud plate 67 and a further annular recess 73 lying rearwardly of theother recess 72, the rear recess 73 being suitably dimensioned toreceive the back plate 63 of the shroud plate 67.

When it is desired to mount the shroud plate 67 within the turbinehousing 71 the front and back plates 66, 63 are inserted into theirrespective recesses 72, 73 with the correct alignment to ensure that thewide tolerance openings 65 correctly overlie the fine tolerance openings64 in the back plate 63 so as to define vane slots extending through thefull thickness of the shroud plate 67 for receipt of vanes attached to anozzle ring as shown in FIGS. 12B and 13B and as now described in moredetail.

FIG. 12B shows a cross-sectional view of a turbine housing with theshroud plate 67 in situ together with a nozzle ring 74 which has anannular array of axially extending vanes 75 attached thereto. Once theback plate 63 and front plate 66 have been received in the respectiverecesses 73, 72 in the turbine housing 71, and correctly aligned, bolts76 or any other suitable fastener are inserted through apertures 70defined by the front plate 66 into axially extending holes 77 defined bythe turbine housing 71. In this way, the front plate 66 is securedagainst the turbine housing 71 so as to substantially prevent anyrelative movement between the front plate 66 and the turbine housing 71.

In contrast to the first and second embodiments of the present inventionin which the three plates 29, 30, 31 making up the shroud plate 27 werelaminated together so as to prevent any relative movement, the backplate 63 of the third embodiment is not fixed to the front plate 66,such that the back plate 63 is permitted to rotate and/or displaceradially relative to the front plate 66 even after having been mountedwithin the turbine housing 71. This is to permit adjustment of thedegree to which the fine tolerance openings 64 in the back plate 63overlie the wider tolerance openings 65 in the front plate 66 whichtogether define the vane slots. This in turn enables the alignment of aparticular set of vane slots with a particular set of vanes 75 attachedto the nozzle ring 74 to be accurately adjusted.

The shroud plate 67 according to the third embodiment of the presentinvention therefore provides a similar benefit in terms of allowing theshroud plate 67 to be formed from a plurality of discs wherein one setof openings is manufactured to a wider tolerance than the other set ofopenings (providing manufacturing and cost benefits as detailed above inrespect of the first and second embodiments) but also the precisealignment of the back plate 63 and therefore the vane slots, can beadjusted after mounting the shroud plate 67 within the turbine housing71, such that fine manufacturing tolerances are only required in respectof the shape of the back plate 63 and the openings 64 rather than theposition of the back plate 63 in the turbine housing 71.

In the third embodiment described above, the back plate 63 lies entirelyaxially behind the front plate 66, but it will be appreciated that itwould be possible to modify the structure of the front and back plates66, 63 such that a part of the plate which can rotate and/or slide maybe located nearer to the front of the shroud plate 67 which faces thegas flowing through the inlet volute 78 of the turbine housing 71. Inthis way, at least some of the fine tolerance openings 64 could beexposed to the gas flowing through the inlet volute rather than the widetolerance openings 65, which would have the benefit of reducingdisturbance to the gas flow.

The back plate 63 may be manufactured from any appropriate material, forexample 304 stainless steel or the like. The front plate 66 may bemanufactured from the same material as the back plate 63, however, itmay be advantageous to employ a material which better suits the thermalexpansion of the material from which the turbine housing 71 ismanufactured (typically iron) since the front plate 66 is bolted to theturbine housing 71. Suitable materials (e.g. for use with an ironturbine housing 71) include 420 stainless steel.

Referring now to FIGS. 14A and 14B, there is shown a fourth embodimentof a shroud plate 79 according to the present invention. The shroudplate 79 again defines an annular array of vane slots 80 defined byopenings 81, 82 in a front plate 83 and a back plate 84 respectively. Inthis embodiment the back plate 84 has a larger outer diameter than thefront plate 83 such that a radially outer annular region 85 of the backplate 84 extends radially beyond the periphery 86 of the front plate 83for reasons that will be explained below in relation to FIGS. 16A to 17.

The cross-sectional shape of the openings 81 in the front plate 83 moreclosely matches the cross-sectional shape of vanes of a nozzle ring (notshown) with which the shroud plate 79 is intended to be used than theopenings 82 in the back plate 84. In this way, the shroud plate 79causes the minimum possible disturbance to gas flowing through an inletvolute of a turbine (not shown) in which the shroud plate 79 is to beused.

In this embodiment the front plate 83 and back plate 84 are eachcomprised of a plurality of discrete segments 88, 89 respectively. Eachsegment 88 in the front plate 83 is secured (for example, by brazing) toits respective axially adjacent segment 89 in the back plate 84 suchthat each pair of axially adjacent segments 88, 89 defines a pair ofaxially overlying openings 81, 82 which combine to define an axiallyextending vane slot 80 as is depicted in FIG. 15.

Each segment 88 of the front plate 83 has curved leading and trailingedges 90, 91 which are connected by curved radially inner and outeredges 92, 93. Similarly, each segment 89 in the back plate 84 has curvedleading and trailing edges 94, 95 connected by curved radially inner andouter edges 96, 97. As can be seen from FIG. 15, each segment 88 in thefront plate 83 is circumferentially offset with respect to thecorresponding segment 89 in the back plate 84. In this way, the leadingand trailing edges 90, 91 of the front segment 88 are positioned furtherforward as compared to the leading and trailing edges 94, 95 of thecorresponding back segment 89. Additionally, each front segment 88 isradially narrower than its corresponding back segment 89 such that theconcave radially inner edge 96 of each back segment 89 lies radiallyinwardly of the concave radially inner edge 92 of each front segment 88,and the convex radially outer edge 97 of each back segment 89 liesradially outwardly of the convex radially outer edge 93 of each frontsegment 88. The concave leading edges 90, 94 and convex trailing edges91, 95 of the front and back plates 88, 89 extend generally radiallyoutwardly. Each curved edge 90, 91, 94, 95 is swept forward of a radialline X (see FIG. 14A) passing through the centre of the shroud plate 79.

The radially inner edges 92, 96 and the radially outer edges 93, 97 ofthe front and back segments 88, 89 are also curved to an appropriateextent, taking into account the desired dimensions of the shroud plate79 and the number of segments 88, 89 forming the shroud plate 79, whichin this embodiment matches the number of vanes on the nozzle ring withwhich the shroud plate 79 is intended to be used. The leading edges 90,94 of each front and back segment 88, 89 are swept forward to a greaterextent than the trailing edges 91, 95 such that each pair of segments88, 89 defines a scimitar-like cross-sectional shape in which theconcave inner edge 92 of the front segment 88 is shorter than the convexradially outer edge 93 of the front segment 88, and the concave radiallyinner edge 96 of the back segment 89 is shorter than the convex radiallyouter edge 97 of the back segment 89.

The segments 88 forming the front plate 83 are circumferentially spacedfrom one another so as to define a small generally radially extendingcircumferential clearance 98A between the leading edge 90 of one segment88A and the trailing edge 91 of a neighbouring segment 88B. Acorresponding generally radially extending clearance 98B is definedbetween each pair of neighbouring segments 89A, 89B in the back plate84. It will be appreciated that the clearances 98A, 98B between eachpair of neighbouring segments 88, 89 in the front and back plates 83, 84might present a leak path for gas flowing through a turbine in which theshroud plate 79 is being used. In order to obviate this problem, eachsegment 88 in the front plate 83 is circumferentially offset compared toits axially adjacent back segment 89 as can clearly be seen in FIG. 15.In this way, the clearances 98A, 98B in the front and back plates 83, 84do not axially overlie. Rather, the clearance 98A between each pair ofsegments 88A, 88B in the front plate 83 is closed by a region of eachback segment 89 which lies axially behind the trailing edge 91 of eachfront segment 88. The clearances 98A, 98B in the front and back plates83, 84 permit radial and rotational displacement of one segment pair88A,89A relative to its neighbouring segment pair 88B, 89B. In this way,each segment pair 88A, 89A can adopt precisely the correct position toreceive a vane (not shown) attached to a nozzle ring (not shown) duringuse.

Referring now to FIGS. 16A, 16B and 17, the shroud plate 79 according tothe fourth embodiment of the present invention is mounted within aturbine housing 100 by receipt of the back plate 84 in an annular recess101 defined by the turbine housing 100 with the front plate 83 beingreceived in a further annular recess 102 defined by the turbine housing100. Once the front and back plates 83, 84 of the shroud plate 79 havebeen received in their respective recesses 102, 101, a retaining ring103 is located towards the radially outer periphery of the shroud plate79 in its own annular recess 104. As can be seen most clearly in FIG.17, the ring 103 extends radially inwardly so as to axially overlie theregion 85 of the back plate 84 which extends radially outwardly of thefront plate 83. In this way, the ring 103 can be used to retain the backplate 84 against the turbine housing 100 and thereby retain the frontplate 83 in place by virtue of each segment 88 in the front plate 83being secured to its respective axially adjacent segment 89 in the backplate 84. The ring 103 defines apertures 105 for receipt of suitablefasteners 106, such as bolts, rivets or the like, which are received inaxially extending holes 107 defined by the turbine housing 100.

After mounting the shroud plate 79 within the turbine housing 100 anozzle ring 108 carrying a plurality of axially extending vanes 109 isthen displaced axially towards the shroud plate 79 such that each vane109 is inserted into its respective vane slot 80 defined by theoverlying pairs of openings 81, 82 in the front and back plates 83, 84.In view of the segmentation of the front and back plates 83, 84 and theclearances 98A, 98B defined between each segment pair 88, 89, thesegment pairs 88, 89 can displace radially and rotationally relative toone another so as to afford the optimum alignment of each segment pair88, 89 with respect to its corresponding vane 109. In this way, the backplate 84 can be manufactured more simply and at lower cost since itneeds only to define relatively wide tolerance openings 82.Additionally, since each opening 81 in the front plate 83 needs to bemanufactured to a fine tolerance only in terms of its cross-sectionalshape, rather than its position relative to the other openings 81, thisallows the relative orientation of the vanes on the nozzle ring to bemanufactured to a wider tolerance thereby simplifying production andreducing cost.

The front and back plates 83, 84 of the shroud plate 79 can bemanufactured from any appropriate material, such as stainless steel. Itmay be advantageous to select a material for at least the back plate 84,if not also the front plate 83, which suits the thermal expansion of theturbine housing 100 during use. Suitable materials include 304 stainlesssteel for the front plate 83 and 420 stainless steel for the back plate84.

While the shroud plate 79 may permit relative rotational and/or radialmovement between pairs of axially adjacent segments 88, 89 in the frontand back plates 83, 84 throughout operation of a turbine incorporatingthe shroud plate 79, the optimum positioning of each segment pair 88, 89may be determined prior to use by insertion of the nozzle ring vanes 109into the vane slots 80, adjustment of the segments 88, 89 to theirmutually optimum positions followed by fixation of each segment pair 88,89 relative to the other segment pairs, for example by brazing. In thisway, the shroud plate 79 would be optimised for a particular nozzle ring108 prior to use and then fixed in this optimum configuration for futureuse.

FIGS. 18A and 18B show a fifth embodiment of a shroud plate 110according to a fifth embodiment. The shroud plate 110 comprises threecoaxial, concentric plates consisting of a rear plate 111, anintermediate segmented plate 112 and a front plate 113. As can be seenfrom FIG. 18A, the intermediate plate 112 defines relatively finetolerance openings 114 which axially overlie larger openings 115, 116 inthe rear and front plates 111, 113 respectively so as to define vaneslots 117 for receipt of vanes in a vane cavity 118 in the same way asthe first four embodiments described above.

In the fifth embodiment, the intermediate segmented plate 112 is made upof an annular array of segments 112 a of generally similar form to thesegments described above in relation to the fourth embodiment. Eachsegment 112 a of the intermediate plate 112 is supported between thefront and rear plates 113, 111 so as to be radially and rotationallydisplaceable with respect to its neighbouring segments 112 b, 112 c. Inthis way, each segment 112 a can adopt the optimum configuration toreceive its respective vane. In the fifth embodiment, the segmentedintermediate plate 112 defines a smaller outer diameter than the rearplate 111, which itself defines a smaller outer diameter than the frontplate 113. The radially outer periphery of the front plate 113 thusextends radially outwardly compared to both the intermediate plate 112and the rear plate 111. The front plate 113 defines a radially extendedportion 119 which defines a tapered aperture 120 for receipt of acountersunk retaining bolt 121. The retaining bolt 121 defines a shaft122 which is of narrower cross-section than the counter bore 123 whichreceives the shaft 122 of the bolt 121. In this way, a clearance isdefined between the shaft of the bolt 122 and the bore 123 toaccommodate thermal expansion flexing of these components.

It can be seen that radial clearances 124, 125 are defined radiallyoutwardly of the intermediate plate 112 and radially inwardly of theplate 112 respectively. Moreover, even though the rear plate 111 definesa larger outer diameter than the intermediate plate 112, the rear plate111 extends radially inwardly to the same extent as the intermediateplate 112 such that the clearance 125 defined between the turbinehousing 126 and the radially inner periphery of the intermediate plate112 is of constant radial dimension and extends axially beyond theradially inner edge of the rear plate 111 towards the turbine housing126.

As shown in FIG. 18B not only are radial clearances 124, 125 definedbeyond the radially outer and inner edges of the intermediate plate 112,but generally radially extending clearances 127 are also defined betweeneach pair of adjacent segments 112 a, 112 b and 112 a, 112 c to affordsufficient clearance to accommodate radial and/or rotation movementbetween the segments 112 a making up the intermediate plate 112.

It will be appreciated that the number of plates used in each of theshroud plates representing different embodiments of the presentinvention described above can be varied from the number described inrespect of each embodiment. For example, the first and secondembodiments in which each plate is fixed to it neighbouring plates arenot limited to using three plates. Rather, two, four, five or moreannular plates may be employed defining annular arrays of openingsoverlying one another so as to define appropriately dimensioned andpositioned vane slots. Moreover, the means by which the shroud plates ofthe first and second embodiments are supported within a turbine housingis not limited to the use of an annular ring extending around thecircumference of the shroud plate. The front plate or plates may have alarger outer diameter than one or more of the back plates, in a similarfashion to the third embodiment described above, such that the frontplate or plates could be fastened to the turbine housing. Alternativelyone or more of the back plates could possess a larger outer diameterthan one or more of the front plates, in a similar fashion to the fourthembodiment, in which case an annular ring or other suitable fastener,such as a bolt, rivet or the like may be used to secure the backplate(s) to the turbine housing to hold the shroud plate in place.

Similarly, the shroud plates according to the third and fourthembodiments described above may incorporate any desirable number ofannular plates and are not limited to using just two plates as describedabove in respect of the specific embodiments. For example, the thirdand/or fourth embodiments may incorporate three, four or more annularplates with annular arrays of openings which overlie one another so asto define appropriately dimensioned and positioned vane slots.

The cross-sectional shape and relative spacing of the vane slots definedby the shroud plates of each embodiment may take any convenient form andis not limited to the exact form depicted in FIGS. 3A to 18B. Moreover,while it is desirable that the fine tolerance openings have across-sectional shape which is very similar to the cross-sectional shapeof the vanes connected to the nozzle ring with which the shroud plate isto be used, it will be appreciated that the size and shape of the widertolerance openings may be varied from that shown in FIGS. 3A to 18B tosuit a particular application and/or to reduce the cost and complexityof the manufacturing process.

1.-91. (canceled)
 92. A variable geometry turbine comprising: a turbinewheel supported in a housing for rotation about a turbine axis; anannular inlet passage defined between respective radial inlet surfacesof first and second wall members, at least one of said first and secondwall members being moveable along the turbine axis to vary the size ofthe inlet passage; an array of vanes extending across the inlet passage,said vanes being connected to said first wall member; a complementaryarray of vane slots defined by the second wall member, said vane slotsbeing configured to receive said vanes to accommodate relative movementbetween the first and second wall members; wherein the second wallmember comprises at least two axially adjacent co-axial plates, a firstof said plates defining a first array of openings which overlie a secondarray of openings defined by a second of said plates so as to definesaid array of vane slots, said first plate being fixed to said secondplate. 93.-97. (canceled)
 98. A turbine according to claim 92, whereinthe second wall member comprises at least a third co-axial plate that isaxially adjacent to said second plate, said third plate defining a thirdarray of openings which overlie the second array of openings defined bythe second plate so as to further define said array of vane slots.
 99. Aturbine according to claim 98, wherein the cross-sectional shapetransverse to said turbine axis of at least one of the openings in saidfirst array of openings more closely matches the cross-sectional shapetransverse to said turbine axis of the vane that said at least oneopening is arranged to receive than the cross-sectional shape transverseto said turbine axis of at least one of the openings in said third arrayof openings.
 100. A turbine according to claim 98, wherein thecross-sectional shape transverse to said turbine axis of at least one ofthe openings in said third array of openings substantially matches thecross-sectional shape transverse to said turbine axis of at least one ofthe openings in said second array of openings.
 101. A turbine accordingto claim 100, wherein said at least one opening in said third array ofopenings axially overlies said at least one opening in said second arrayof openings to further define one slot of said array of vanes slots.102. A turbine according to claim 98, wherein one of said second andthird plates defines at least one further axially extending projectionconfigured for receipt in a complementary recess defined by the other ofthe second and third plates.
 103. A turbine according claim 98, whereinsaid second wall member defines a circumferential groove extendingaround the radially outermost edge of the second wall member, saidgroove arranged to receive a locating ring to retain the second wallmember within the turbine housing.
 104. A turbine according to claim103, wherein the first and third plates possess larger respectivediameters than the second plate, such that the difference in thediameters of the three plates at least partly defines saidcircumferential groove.
 105. A turbine according to claim 98 wherein thethird plate is fixed to the second plate.
 106. A turbine according toclaim 105, wherein the third plate is laminated to the second plate.107. A turbine according to claim 105, wherein the third plate is fixedto the second plate by an adhesive, braze, rivet, screw, or weld.108.-112. (canceled)
 113. A turbine according to claim 92, wherein saidfirst plate comprises first and second segments defining respectivefirst and second openings from said first array of openings, said firstsegment being displaceable relative to said second segment within amajor plane of the first plate.
 114. A turbine according to claim 113,wherein each of said segments comprises generally radially extendingleading and trailing edges connected by radially inner and outer edges.115. (canceled)
 116. A turbine according to claim 114, wherein saidsecond plate comprises first and second segments defining respectivefirst and second openings from said second array of openings, said firstsegment of the second plate being displaceable relative to said secondsegment of the second plate within a major plane of the second plate.117. A turbine according to claim 116, wherein said first segment of thefirst plate axially overlies said first segment of the second plate.118. A turbine according to claim 116, wherein each of said segments ofthe second plate comprises generally radially extending leading andtrailing edges connected by radially inner and outer edges.
 119. Aturbine according to claim 118, wherein a clearance is defined betweenthe leading edge of one segment of the first plate and the trailing edgeof a neighbouring segment of the first plate.
 120. A turbine accordingto claim 119, wherein a further clearance is defined between the leadingedge of one segment of the second plate and the trailing edge of aneighbouring segment of the second plate.
 121. A turbine according toclaim 120, wherein said first segment of the second plate iscircumferentially offset with respect to said first segment of the firstplate such that said clearance defined between segments of the firstplate is circumferentially offset with respect to said further clearancedefined between segments of the second plate. 122.-126. (canceled) 127.A variable geometry turbine comprising: a turbine wheel supported in ahousing for rotation about a turbine axis; an annular inlet passagedefined between respective radial inlet surfaces of first and secondwall members, at least one of said first and second wall members beingmoveable along the turbine axis to vary the size of the inlet passage;an array of vanes extending across the inlet passage, said vanes beingconnected to said first wall member; a complementary array of vane slotsdefined by the second wall member, said vane slots being configured toreceive said vanes to accommodate relative movement between the firstand second wall members; wherein the second wall member comprises afirst plate defining a first array of openings so as to define saidarray of vane slots, said first plate comprising first and secondsegments defining respective first and second openings from said firstarray of openings, said first segment being displaceable relative tosaid second segment within a major plane of the first plate. 128.-129.(canceled)
 130. A turbine according to claim 127, wherein the secondwall member comprises a second plate which is positioned axiallyadjacent to the first plate and said second plate being arrangedco-axially with respect to said first plate, the first plate defining afirst array of openings which overlie a second array of openings definedby the second plate so as to define said array of vane slots.
 131. Aturbine according to claim 130, wherein said second plate comprisesfirst and second segments defining respective first and second openingsfrom said second array of openings, said first segment of the secondplate being displaceable relative to said second segment of the secondplate within a major plane of the second plate.
 132. A turbine accordingto claim 131, wherein said first segment of the first plate axiallyoverlies said first segment of the second plate.
 133. A turbineaccording to claim 131, wherein each of said segments of the secondplate comprises generally radially extending leading and trailing edgesconnected by radially inner and outer edges.
 134. A turbine according toclaim 133, wherein a clearance is defined between the leading edge ofone segment of the first plate and the trailing edge of a neighbouringsegment of the first plate.
 135. A turbine according to claim 134,wherein a further clearance is defined between the leading edge of onesegment of the second plate and the trailing edge of a neighbouringsegment of the second plate.
 136. A turbine according to claim 135,wherein said first segment of the second plate is circumferentiallyoffset with respect to said first segment of the first plate such thatsaid clearance defined between segments of the first plate iscircumferentially offset with respect to said further clearance definedbetween segments of the second plate. 137.-145. (canceled)